CN101769165A - Positive displacement gas turbine engine with parallel screw rotors - Google Patents
Positive displacement gas turbine engine with parallel screw rotors Download PDFInfo
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- CN101769165A CN101769165A CN200910113700A CN200910113700A CN101769165A CN 101769165 A CN101769165 A CN 101769165A CN 200910113700 A CN200910113700 A CN 200910113700A CN 200910113700 A CN200910113700 A CN 200910113700A CN 101769165 A CN101769165 A CN 101769165A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C1/00—Rotary-piston machines or engines
- F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
- F01C1/12—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
- F01C1/14—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
- F01C1/16—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type
- F01C1/165—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type having more than two rotary pistons with parallel axes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C1/00—Rotary-piston machines or engines
- F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
- F01C1/12—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
- F01C1/14—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
- F01C1/20—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with dissimilar tooth forms
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C11/00—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
- F01C11/002—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C29/00—Component parts, details or accessories of pumps or pumping installations, not provided for in groups F04C18/00 - F04C28/00
- F04C29/12—Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
- F01C11/00—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
- F01C11/006—Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of dissimilar working principle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C2240/00—Components
- F04C2240/20—Rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C2250/00—Geometry
- F04C2250/10—Geometry of the inlet or outlet
- F04C2250/101—Geometry of the inlet or outlet of the inlet
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C2250/00—Geometry
- F04C2250/10—Geometry of the inlet or outlet
- F04C2250/102—Geometry of the inlet or outlet of the outlet
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a positive displacement gas turbine engine with parallel screw rotors. An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.
Description
Technical field
The present invention relates generally to positive displacement (positive displacement) rotating machinery and motor and their member, and relates more specifically to have this class machinery and member of main rotor and gate rotor (gaterotor).
Background technique
Axial flow positive displacement rotating machinery has been used for pump, turbine, compressor and motor, and is commonly referred to as and is screw pump, screw type turbine and screw compressor.Disclosed is that the positive displacement rotating machinery with main rotor and gate rotor can be used for turbine and compressor.The member of blade, for example fan in various types of gas turbine engines, compressor and turbine radially are equipped with in the common use of axial flow turbine.Axial flow turbine is with a wide range of applications aspect the energy using the energy acting or obtain from working fluid, because the integration capability that the oriented given proparea of axial flow turbine (frontal area) provides high mass velocity and continuous approaching stable fluid to flow.Turbine design person's target is the turbine components or machinery and the motor that provide in light weight and compact.Another target is to make turbine to have the least possible part, makes, installs, rebuilds, overhauls and change the cost of member or machinery to reduce.
Summary of the invention
The member of axial flow positive displacement gas turbine engine comprises the rotor assembly that extends to axially spaced axial flow outlet from holoaxial streaming inlet downstream, and comprises main rotor and one or more gate rotor.Main axis and lock axis that main rotor and gate rotor can be respectively depart from around the almost parallel ground of main rotor and gate rotor rotate.Main rotor and gate rotor have respectively the intermeshing main helical blade and the lock helical blade of reeling around main axis and lock axis, and main helical blade and lock helical blade radially outwards extend from being defined as around the annular main wheel hub and the circular brake wheel hub of main axis and lock axis.
An exemplary embodiment of member comprises the main loop opening and the lock annular opening that intersect that radially extends respectively between the housing that holds rotor assembly and main wheel hub and brake wheel hub.Gearing (gearing) makes main rotor and gate rotor synchronous together.
The middle body of main helical blade extends vertically and downstream, and has the overall diameter that radially outwards records from the main wheel hub to height.The inlet changeover portion is positioned at the axial the place ahead and the upstream of middle body.In the inlet changeover portion, main helical blade carries out the transition to fully the blade profile that launches from 0 radial height on downstream direction, and this blade profile that launches fully has from the radially measured overall diameter of main wheel hub to height.
Member can have the outlet changeover portion in the axial rearward direction of middle body and downstream, and wherein, main helical blade carries out the transition to from 0 radially measured radial height of main wheel hub to the blade profile that launches fully of height from having overall diameter on downstream direction.
Main helical blade and lock helical blade can rotate in stream, and this stream is disposed radially between main wheel hub and brake wheel hub and housing, and extend to the axial flow outlet vertically downstream from the axial flow inlet.Stream comprises inlet flowpath segment, the annular central flowpath segment that is arranged in the inlet changeover portion with crossfire relation downstream, and is arranged on the outlet flowpath segment in the outlet changeover portion.The annular entry area of inlet flowpath segment is less than the annular exit area of inlet flowpath segment.The outlet flowpath segment also can have the circular crosssection area that reduces on downstream direction.
The main helical blade of rotor assembly respectively first section of rotor assembly with second section in have the different first main slope (slope) and second that reverses and lead and reverse slope, and the lock helical blade respectively this first section with second section in have that the first different locks reverses slope and second lock reverses slope.
A compressor that embodiment is an axial flow positive displacement gas turbine engine of axial flow positive displacement gas turbine engine member, wherein, first main slope and first lock of reversing reverses slope and mainly reverses slope and second lock reverses slope less than second respectively.Another embodiment of axial flow positive displacement gas turbine engine member is the turbine of axial flow positive displacement gas turbine engine, and wherein, first main slope and first lock of reversing reverses slope and mainly reverse slope and second lock reverses slope greater than second respectively.
Description of drawings
Fig. 1 is the perspective view with axial flow inlet positive-displacement compressor of a main rotor and a gate rotor.
Fig. 2 is the main rotor of the rotor assembly of compressor shown in Fig. 1 and the respectant perspective view of the past of gate rotor.
Fig. 3 be the main rotor of the rotor assembly shown in Fig. 1 and gate rotor from the forward-looking perspective view in back.
Fig. 4 is first compressing section and the main rotor of second compressing section and the perspective view of seeing from the top down of gate rotor through rotor assembly shown in Fig. 2.
Fig. 5 is the perspective view of seeing from the side of the main rotor in the compressing section of rotor assembly shown in Fig. 2.
Fig. 6 is the perspective view of seeing from the side of the gate rotor in the compressing section of rotor assembly shown in Fig. 2.
Fig. 7 is the main rotor with three helical blades or blade profile part of compressor shown in Fig. 2 and Fig. 3 and the sectional view of the vane collocation (blading) of the gate rotor with four helical blades or blade profile part (lobe).
Fig. 8 is the perspective view of compressing section with rotor shaft streaming inlet positive-displacement compressor of main rotor and two gate rotors.
Fig. 9 is the main rotor of rotor assembly shown in Fig. 8 and the perspective view of two gate rotors.
Figure 10 is the perspective view that leading edge is seen downstream that scans of main rotor helical blade in the suction port of compressor changeover portion shown in Fig. 8 and Fig. 9.
Figure 11 is the perspective view that leading edge is seen from the side that scans of main rotor helical blade shown in Figure 10.
Figure 12 is the perspective view of the helical blade trailing edge of main rotor in the outlet changeover portion of compressor shown in Fig. 8 and Fig. 9.
Figure 13 is having with the main rotor of four helical blades or blade profile part and the cross-sectional of arranging with the alternative blade of the rotor assembly of the gate rotor of three helical blades or blade profile part shown in Fig. 8.
Figure 14 is having with the main rotor of six helical blades or blade profile part and the cross-sectional of arranging with the alternative blade of the rotor assembly of the gate rotor of four helical blades or blade profile part shown in Fig. 8.
Figure 15 is having with the main rotor of eight helical blades or blade profile part and the sectional view arranged with the alternative blade of the gate rotor of five helical blades or blade profile part shown in Fig. 8.
Figure 16 is the cross-sectional of gearing of the rotor assembly of the compressor shown in Fig. 1.
Figure 17 is the cross-sectional of gearing of the rotor assembly of the compressor shown in Fig. 8.
Figure 18 is the cross-sectional with axial flow inlet positive displacement expander (expander) of a main rotor and a gate rotor.
Figure 19 is the cross-sectional with axial flow inlet positive displacement expander of main rotor and two gate rotors.
Figure 20 is the respectant perspective view of the past of scanning leading edge of the main rotor helical blade in the inlet of expander shown in Figure 18 changeover portion.
Figure 21 is the respectant perspective view of the past of the main rotor helical blade trailing edge in the outlet of expander shown in Figure 18 and Figure 20 changeover portion.
Figure 22 is the side perspective view of the helical blade trailing edge of main rotor in expander shown in Figure 22 outlet changeover portion and gate rotor.
Figure 23 is the cross-sectional of rotor assembly with compressor of two main rotors and a gate rotor.
Figure 24 is the cross-sectional of rotor assembly with compressor of two main rotors and two gate rotors.
Figure 25 is the sectional view of the vane collocation of the main rotor of compressor shown in Figure 23 and gate rotor.
Figure 26 is the sectional view of vane collocation of rotor assembly that has the compressor of two main rotors and a gate rotor, and these two main rotors and a gate rotor have the not axis in a plane.03789101112131415161718192021222324252627282930323334353637394041434445474849505153555758596768697072747678798082848890929496100102117124126131170209217230232235AIAOACCLCCCCACDCPCSDHRMRG
Embodiment
This paper shows the exemplary embodiment of compressor 8 (shown in Fig. 1 to Figure 17), turbine or the expander 88 (shown in Fig. 8 to Figure 22) of axial flow inlet positive displacement gas turbine engine, they have main rotor and one or more gate rotor, and representative has the axial flow positive displacement gas turbine engine member 3 of main rotor and one or more gate rotors.Axial flow positive displacement gas turbine engine member designs with main rotor 12 and one or more gate rotors 7 becomes in order to acting, as energy is for example entered into the working fluid 25 of continuous-flow via compressor 8, perhaps from the working fluid 25 of continuous-flow, obtain energy, as axial flow positive displacement expander or turbine.
Fig. 1 to Fig. 7 shows the exemplary embodiment of the compressor 8 of the axial flow inlet positive displacement gas turbine engine that has main rotor 12 and gate rotor 7 in compressor housing 9.Compressor 8 has rotor assembly 15, and it comprises main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from holoaxial streaming inlet 20.Compressor housing 9 holds main rotor 12 and gate rotor 7.Fig. 8 to Figure 15 shows second exemplary embodiment of the compressor 8 of axial flow inlet positive displacement gas turbine engine, wherein, rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow inlet 20, comprises the main rotor 12 and first gate rotor 13 and second gate rotor 14.
Be the rotor assembly 15 with main rotor 12 and single gate rotor 7 of compressor 8 shown in Fig. 2 to Fig. 6.Rotor assembly 15 comprises the intermeshing main helical blade 17 and the lock helical blade 27 of reeling around the parallel main axis 16 and the lock axis 18 of main rotor 12 and gate rotor 7 respectively.Shown in concrete among Fig. 2, main helical blade 17 and lock helical blade 27 extend radially outward from main wheel hub 51 and brake wheel hub 53, and wherein, main wheel hub 51 and brake wheel hub 53 are defined as respectively around main axis 16 and lock axis 18.The different first main slope 34 and second that reverses that first compressing section 24 of the rotor assembly 15 of compressor 8 and second compressing section 26 have main helical blade 17 mainly reverses slope 36, and the first different lock of lock helical blade 27 reverses slope 32 and second lock reverses slope 35.Reverse the pitch of slope, and describe in more detail hereinafter corresponding to the helical blade of rotor as herein described.The middle body 170 that extends through the main helical blade 17 of first compressing section 24 and second compressing section 26 vertically and downstream have with from main wheel hub 51 to housing the measured overall diameter of 9 radially outside modes to height H.
Have the constant first main slope 34 and second that reverses in main helical blade 17 and lock helical blade 27 each person in first compressing section 24 and second compressing section 26 respectively and mainly reverse slope 36 and the first constant lock reverses slope 32 and second lock reverses slope 35.The first main slope 34 and second that reverses mainly reverses slope 36 and differs from one another, and first lock reverses slope 32 and second lock and reverses slope 35 and also differ from one another.Reverse slope and be defined as the rotating amount of the cross section 41 of helix element (main lobe type spare 57 as shown in Figure 7) along the per unit distance of axis such as main axis 16.As shown in Fig. 2 and Fig. 4, reverse slope and be 360 degree or 2Pi radian divided by along the axial distance CD between two adjacent top 44 of the identical main helical margin 47 of helix element (for example, main helical blade 17 as shown in Figure 2 or lock helical blade 27) or lock helical margin 48.Axial distance CD is the distance of whole circle 43 helicals.In compressor, first in first section 24 reverses slope and reverses slope less than second in second section 26.
As shown in Fig. 2 and Fig. 3, compressor 8 includes mouthful changeover portion 28 and outlet changeover portion 30, and they are positioned at the upstream and downstream of first compressing section 24 and second compressing section 26 respectively and are designed to the axial flow of passing compressor 8 in order to hold.First compressing section 24 of rotor assembly 15 and compressor 8 and second compressing section 26 are positioned between inlet changeover portion 28 and the outlet changeover portion 30 with crossfire relation downstream.In inlet changeover portion 28, main helical blade 17 carries out the transition to fully the blade profile that launches, become from 0 radial height on the downstream direction D from main wheel hub 51 radially outwards and on axial downstream D measured overall diameter to height H.In outlet changeover portion 30, the blade profile transition of main helical blade 17 from launching fully becomes from 0 radially measured radial height of main wheel hub 51 to height H from overall diameter on downstream direction D.Inlet changeover portion 28 helps to provide the full axial flow via axial flow inlet 20, and outlet changeover portion 30 helps to provide the full axial flow via axial flow outlet 22.
Referring to Fig. 2, stream 40 is disposed radially between main wheel hub 51 and brake wheel hub 53 and housing 9 (shown in Fig. 1), and axially extends to axial flow outlet 22 downstream from axial flow inlet 20.Main helical blade 17 and lock helical blade 27 can rotate in stream 40.Stream 40 also comprises the main rotor stream 45 that roughly holds main rotor 12, and main helical blade 17 can rotate in main rotor stream 45.Stream 40 comprises the annular central flowpath segment 70 for main rotor 12.Annular central flowpath segment 70 is disposed radially between main wheel hub 51 and housing 9, and axially extends between inlet changeover portion 28 and outlet changeover portion 30.Stream 40 comprises the inlet flowpath segment 76 that is arranged in the inlet changeover portion 28, is arranged on the annular central flowpath segment 70 in first compressing section 24 and second compressing section 26 with downstream crossfire relation, and is arranged on the outlet flowpath segment 78 in the outlet changeover portion 30.
It is the fully blade profile of expansion of overall diameter to height H that main helical blade 17 and lock helical blade 27 have in first compressing section 24 and second compressing section 26, and through first compressing section 24 and second compressing section 26 and compressor housing 9 sealing engagement (sealing between main helical blade 17 and lock helical blade 27 and the housing 9 has been shown among Fig. 7).Main helical blade 17 and lock helical blade 27 rotate through inlet flowpath segment 76, annular central flowpath segment 70 and outlet flowpath segment 78 respectively.Inlet flowpath segment 76, annular central flowpath segment 70 and outlet flowpath segment 78 are separately positioned between compressor housing 9 and main wheel hub 51 and the brake wheel hub 53.Inlet flowpath segment 76, annular central flowpath segment 70 and outlet flowpath segment 78 form compressor stream 40, and this compressor stream 40 axially and along downstream direction D extends to axial flow outlet 22 from axial flow inlet 20.
First compressing section 24 is designed to whole volumes of filling air 50 in order to seal, and makes it export 22 with axial flow inlet 20 and axial flow to keep apart.In case capture, then fluid filled air 50 just passes pressure planes CP and enters in second compressing section 26 as discharge areas, and the axial dimension of filled volume can reduce and radial dimension may also can reduce.Fluid filled air 50 is discharged into the static stream 131 shown in Fig. 1 and Fig. 2 from the outlet changeover portion 30 in 26 downstreams, second compressing section then.Under the enough low situation of outlet Mach number, can omit outlet changeover portion 30, allow that rotor carries out the transition to static stream sharp.
Main rotor and gate rotor can rotate around its corresponding axis, and can go up rotation at different circumferencial direction (C and counter-clockwise CC clockwise) by the determined rotating speed of fixed relationship as shown in Figure 16.Therefore, main rotor 12 and gate rotor 7 link together with gear, so as they always with as shown in figs. 1 and 4 and fixing speed ratio and the phase relationship that provided of the gearing 80 in the gear-box 82 that in Figure 16, schematically shows relative to each other rotate.Main rotor 12 can rotate around main axis 16, and gate rotor 7 can be around 18 rotations of lock axis.Power in order to Driven Compressor 8 can be supplied with via line shaft 37, and in Fig. 1, Fig. 4 and Figure 16, line shaft 37 is shown and is connected on the main rotor 12.Gate rotor 7 and main rotor 12 timing gear 84 by the gearing in the gear-box 82 80 links together with gear, providing, and between their main helical blade 17 and the lock helical blade 27 of engagement, have minimum and controlled gap to rotor rotation suitably regularly.
Show main rotor 12 and gate rotor 7 among Fig. 4 to Fig. 6 respectively and center on main axis 16 and the intermeshing main helical blade 17 and the lock helical blade 27 of lock axis 18 coilings.Main helical blade 17 and lock helical blade 27 have main helicoid 21 and lock helicoid 23 respectively.Between inlet changeover portion 28 and outlet changeover portion 30, main helical blade 17 radially outwards extends from the ring surface CS of the annular main wheel hub 51 of main rotor 12.Lock helical blade 27 radially outwards extends from the brake wheel hub 53 of gate rotor 7.Ring surface CS and annular main wheel hub 51 are shown taper shape, but also can be such as columniform other shape.
The cylndrical surface CS of main wheel hub 51 axially extends between main helical blade 17.Main helical margin 47 engages when they relative to each other rotate with the lock helicoid 23 of lock helical blade 27 hermetically along main helical blade 17.Lock helical margin 48 engages when they relative to each other rotate with the main helicoid 21 of main helical blade 17 hermetically along lock helical blade 27.Main wheel hub 51 and brake wheel hub 53 are straight in the axial direction, and are defined as around main axis 16 and lock axis 18.Main wheel hub and brake wheel hub can be hollow or solid.
When axially observing, main helical blade 17 and lock helical blade 27 take it is as shown in Figure 7 main lobe type spare 57 and lock blade profile part 67 as.Exemplary compressor 8 shown in Fig. 1 to Fig. 7 has three main lobe type spares 57 and four lock blade profile parts 67.Less body clearance CL remains between compressor housing 9 (shown in the dotted line among Fig. 7) and main rotor 12 and the gate rotor 7.Self passing through as mentioned between main rotor 12 and gate rotor 7, the timing gear 84 of disclosed gear-box 82 keeps less axial clearance AC (shown in Fig. 4).For the assembly 15 of two rotors, the number of lock blade profile part is than the number one more or less of main lobe type spare.Main radius R M and lock radius R the G overall diameter of the lock helical blade 27 of the main helical blade 17 from main axis 16 and lock axis 18 to main rotor 12 and gate rotor 7 respectively record to height H.The length that main radius R M and lock radius R G can have about equally or not wait.Main radius R M is shown longer than lock radius R G in Fig. 7.
Shown in Fig. 8 is the compressor 8 of exemplary shaft streaming inlet positive displacement gas turbine engine, and it has a main rotor and two or more gate rotor, and it represents the member 3 of axial flow inlet positive displacement gas turbine engine.Compressor 8 shown in Fig. 8 and Fig. 9 has main rotor 12 and first gate rotor 13 and second gate rotor 14.Referring to Fig. 9, compressor 8 has first compressing section 24 and second compressing section 26 between inlet changeover portion 28 and outlet changeover portion 30.Inlet changeover portion 28, first compressing section 24 and second compressing section 26, and export 30 one-tenth crossfires relations downstream of changeover portion, and be designed to flow to continuously vertically and pass the working fluid 25 of compressor 8 in order to compression.Have different first respectively and reverse slope 34 and second and reverse slope 36 with second section 26 for first section 24.As indicated above, reverse the pitch of slope corresponding to the helical blade of rotor.
Referring to Fig. 8 and Fig. 9, comprise rotor assembly 15 at the compressor shown in this 8, this rotor assembly 15 has main rotor 12 and first gate rotor 13 and second gate rotor 14 that extends to outlet 22 from axial flow inlet 20.Main rotor 12 has respectively and the first lock helical blade 27 of first gate rotor 13 and the second lock helical blade, the 29 intermeshing main helical blades 17 of second gate rotor 14.Main helical blade 17 radially outwards extends from the annular main wheel hub 51 of main rotor 12, and this annular main wheel hub 51 is defined as around main axis 16.The first lock helical blade 27 and the second lock helical blade 29 radially outwards extend from the first brake wheel hub 53 and the second brake wheel hub 55 of the annular of first gate rotor 13 and second gate rotor 14, and this first brake wheel hub 53 and the second brake wheel hub 55 are defined as respectively around the first lock axis 19 and the second lock axis 39.
Referring to Fig. 8 to Figure 12, rotor assembly 15 includes mouthful changeover portion 28 and outlet changeover portion 30, to hold the axial flow through compressor 8.More specifically illustrate as Figure 10 and Figure 11, main helical blade 17 has leading edge 117, and it carries out the transition to the blade profile that launches fully in changeover portion 28 at inlet, from 0 radial height become as from main wheel hub 51 and along the measured overall diameter of downstream direction D to height H.Term " blade profile of Zhan Kaiing fully " is defined as from the measured overall diameter of main wheel hub 51 to height H.As more specifically illustrating among Figure 12, main helical blade 17 has trailing edge 217, and it is the blade profile transition from launching fully in outlet changeover portion 30, becomes as from 0 measured radial height of main wheel hub 51 to height H from overall diameter.An alternative of compressor 8 does not comprise outlet changeover portion 30.
As shown in Figure 10, main helical blade 17 parts of passing inlet changeover portion 28 are leading edge 117, and can be described as helical, and scan backward or downstream.Scanning leading edge 117 is separated to the mass flow that enters in the rotor channel that launches fully reposefully.For using for the member designs of the high rotor wheel speed that has over-one Mach number in the rotor relative reference system, what this section can occupy whole compressor or member length is not very little part.
Fig. 8 and Fig. 9 show the compressor 8 of the axial flow inlet positive displacement gas turbine engine with rotor assembly 15, this rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow inlet 20, comprises the main rotor 12 and first gate rotor 13 and second gate rotor 14.Axial flow inlet 20 comprises the main loop opening 10 and the lock annular opening 11 that intersect that radially extends respectively between compressor housing 9 and main wheel hub 51 and brake wheel hub 53.Stream 40 is disposed radially between main wheel hub 51 and brake wheel hub 53 and housing 9, and axially extends to axial flow outlet 22 downstream from axial flow inlet 20.
Extension between the inlet flowpath segment 76 that is used for main rotor shown in Fig. 8 and Figure 11 is via the annular entry housing face 92 of inlet changeover portion 28 at the annular entry wheel hub surface 90 of main wheel hub 51 and brake wheel hub 53 and housing 9.Annular entry wheel hub surface 90 and annular entry housing face 92 are shown taper shape, but also can be such as columniform other shape.Inlet flowpath segment 76 has circular crosssection area CA, and it increases along downstream direction D or the past direction backward.Therefore, the annular entry area A I of inlet flowpath segment 76 is less than the annular exit area A O of inlet flowpath segment 76.Outlet flowpath segment 78 is via the extension between the annular exit housing face 96 of the annular exit wheel hub surface 94 of main wheel hub 51 and brake wheel hub 53 and housing 9 of outlet changeover portion 30.Annular exit wheel hub surface 94 and annular exit housing face 96 are shown taper shape, but also can be such as columniform other shape.Outlet flowpath segment 78 has circular crosssection area CA, and it reduces along downstream direction D or the past direction backward.Therefore, the annular entry area of outlet flowpath segment 78 is greater than the annular exit area A O of outlet flowpath segment 78.Inlet flowpath segment 76 and outlet flowpath segment 78 help to provide the full axial flow that runs through compressor 8, comprise passing axial flow inlet 20 and axial flow outlet 22.
Referring to Fig. 8 and Figure 11, first compressing section 24 of rotor assembly 15 and compressor 8 and second compressing section 26 are positioned between inlet changeover portion 28 and the outlet changeover portion 30 with crossfire relation downstream.Rotor assembly 15 provides via the Continuous Flow of inlet 20 with outlet 22 at compressor 8 duration of works.Independent filling air 50 is captured and is trapped in wherein by first section 24.Inflation 50 compression is along with inflation is passed to second section 26 and take place from first section 24.Therefore, all filling air 50 all is compressed when it is in first section 24 and second sections 26 respectively in the two.
Main rotor and gate rotor all can be around its corresponding axis rotations, and main rotor 12 can be different from first gate rotor 13 and second gate rotor 14 circumferencial direction but with by the determined same rotational speed rotation of fixed relationship.As shown in Figure 16, main rotor 12 is shown and can turns clockwise, and first gate rotor 13 and second gate rotor 14 are shown and can rotate by counter-clockwise CC.Therefore, main rotor 12, first gate rotor 13 and second gate rotor 14 link together with gear, make them always relative to each other rotate with fixing speed ratio and the phase relationship that the gearing 80 that schematically shows among Figure 17 is provided.Power in order to Driven Compressor 8 can be supplied with via line shaft 37, and line shaft 37 is shown and is connected on the main rotor 12, as shown in Figure 17.First gate rotor 13 and second gate rotor 14 timing gear 84 by gearing 80 links together with gear, providing, and between their spiral form master helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29 of engagement, have minimum and controlled gap to rotor rotation suitably regularly.
Referring to Fig. 9 and Figure 11, main helical blade 17 has main helicoid 21, and the first lock helical blade 27 and the second lock helical blade 29 have the first lock helicoid 23 and the second lock helicoid 33 respectively.Main helical blade 17 radially outwards extends from the cylndrical surface CS of the annular main wheel hub 51 of main rotor 12.The first lock helical blade 27 and the second lock helical blade 29 radially outwards extend from the first brake wheel hub 53 and the second brake wheel hub 55.
The cylndrical surface CS of main wheel hub 51 axially extends between main helical blade 17.Main helical margin 47 engages respectively when they relative to each other rotate with first lock helicoid 23 of the first lock helical blade 27 and the second lock helicoid 33 of the second lock helical blade 29 hermetically along main helical blade 17.The first lock helical margin 48 and the second lock helical margin 49 engage when they relative to each other rotate with the main helicoid 21 of main helical blade 17 hermetically along the first lock helical blade 27 and the second lock helical blade 29.The first brake wheel hub 53 and the second brake wheel hub 55 are defined as respectively around the first lock axis 19 and the second lock axis 39, and are defined as brake wheel hub around the lock axis in the axial direction for straight.Main wheel hub and brake wheel hub can be hollow.
The main rotor 12, first gate rotor 13 and second gate rotor 14 that are used for the blade structure of rotor shown in Fig. 8 and Fig. 9 have been shown in the axial cross section in Figure 13.As shown in Figure 13, main rotor 12, first gate rotor 13 and second gate rotor 14 have lock blade profile part 67, the first rotor blade profile part 68 and the second rotor blade profile part 69 that corresponds respectively to main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29.Housing 9 is shown in broken lines.If main rotor 12 has M main lobe type spare 57 or main helical blade 17, and first gate rotor 13 and second gate rotor 14 have N the first rotor blade profile part 68 or the first lock helical blade 27 and N the second rotor blade profile part 69 or the second lock helical blade 29, then N the first rotor blade profile part 68 and the second rotor blade profile part 69 are N=M/2+1 just, and N and M are integer.This relation of N and M is used for the structure of three rotors.Therefore, M=4 and N=3 is used for the structure shown in Fig. 8, Fig. 9 and Figure 13.The constructive alternative of main rotor 12, first gate rotor 13 and second gate rotor 14 is shown with section form has M=6 and N=4 in Figure 14, and is M=8 N=5 in Figure 15.
Referring to Fig. 9, the main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29 have constant first respectively and reverse slope 34 and second and reverse slope 36 in first section 24 and second sections 26.Reverse cross section 41 that slope is defined as helix element (comprising the lock blade profile part 67 shown in Figure 13 to Figure 15, the first rotor blade profile part 68 and the second rotor blade profile part 69) at rotating amount along the per unit distance of axis (main axis 16 as shown in Figure 9).Main rotor cross section 41 has been shown among Fig. 9 has revolved three-sixth turn.
Reverse slope and also be 360 degree or 2Pi radian divided by along the axial distance CD between two adjacent top 44 of the identical main helical margin 47 of helix element (for example, main helical blade 17 as shown in Figure 9 and lock helical blade 27) and lock helical margin 48.Axial distance CD is the distance of whole circle 43 helicals.For compressor, in first section 24 first reverses slope 34 and reverses slope 36 less than second in second section 26, in second section 26 second reverses slope 36 and is shown in Fig. 2 and is used for single gate rotor structure, but also is applicable to the structure with two or more gate rotors.
Figure 16 and Figure 17 schematically show the embodiment 100 of two rotors of axial flow positive-displacement compressor 8 and the embodiment 102 of three rotors respectively.The embodiment 100 of two rotors as indicated above has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from axial flow inlet 20.The axial flow of working fluid 25 is represented by arrow.The embodiment 102 of three rotors as indicated above has rotor assembly 15, and this rotor assembly 15 has three rotors that extend to axial flow outlet 22 from axial flow inlet 20, comprises the main rotor 12 and first gate rotor 13 and second gate rotor 14.
Schematically show the embodiment 100 of two rotors of axial flow positive displacement turbine or expander 88 and the embodiment 102 of three rotors among Figure 18 and Figure 19.The embodiment 100 of two rotors of expander 88 has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and the gate rotor 7 that extends to axial flow outlet 22 from axial flow inlet 20.The embodiment 102 of three rotors of expander 88 has rotor assembly 15, and this rotor assembly 15 has main rotor 12 and first gate rotor 13 and second gate rotor 14 that extends to axial flow outlet 22 from axial flow inlet 20.
Power obtains from expander 88 via line shaft 37, and as shown in Figure 17 and Figure 18, line shaft 37 is shown to be connected on the main rotor 12 and from main rotor 12 and extends backward or downstream, but also can extend forward or upstream from main rotor 12.Gate rotor is connected on the main rotor by the timing gear 84 of gearing 80, providing, and between their main helical blade 17 and the first lock helical blade 27 and the second lock helical blade 29 of engagement, have minimum and controlled gap to rotor rotation suitably regularly.
As shown in Figure 21, for the embodiment 100 of two rotors shown in Figure 18, expander 88 has inlet flowpath segment 76 and axial flow inlet 20, and axial flow inlet 20 comprises in crossing the main loop opening 10 and lock annular opening 11 between the brake wheel hub 53 of the main wheel hub 51 that is each defined in expander housing 209 and main rotor 12 and gate rotor 7.Expander shown here also has the axial flow outlet 22 of the outlet flowpath segment 78 that has shown in Figure 21 and Figure 22.Inlet flowpath segment 76 shown in Figure 20 is via the axially extension between the annular entry housing face 92 of the annular entry wheel hub surface 90 of the corresponding main wheel hub 51 of main rotor 12 and gate rotor 7 and brake wheel hub 53 and housing 209 of inlet changeover portion 28.Annular entry wheel hub surface 90 and annular entry housing face 92 are shown taper shape, but also can be such as columniform other shape.Inlet flowpath segment 76 has circular crosssection area CA, and it increases along downstream direction D or the past direction backward.Therefore, the annular entry area A I of inlet flowpath segment 76 is less than the annular exit area A O of inlet flowpath segment 76.
In inlet changeover portion 28, main helical blade 17 carries out the transition to fully the blade profile that launches, become from 0 radial height on the downstream direction D from main wheel hub 51 radially outwards and on axial downstream D measured overall diameter to height H.Lock helical blade 27 carries out the transition to fully the blade profile that launches, become from 0 radial height on the downstream direction D from brake wheel hub 53 radially outwards and on axial downstream D measured overall diameter to height.
In outlet changeover portion 30, the blade profile transition of main helical blade 17 from launching fully becoming from main wheel hub 51 0 measured radial height outwards and on axial downstream D radially to height H from overall diameter on the downstream direction D.Lock helical blade 27 is the blade profile transition from launching fully also, is becoming from main wheel hub 51 0 measured radial height outwards and on axial downstream D radially to height H from overall diameter on the downstream direction D.
As shown in Figure 21, the trailing edge 217 that extends through the main helical blade 17 of outlet changeover portion 30 can be described as helical, and scans backward or downstream.Scanning trailing edge 217 helps to prevent to separate and prevent that eddy current from leaving the helical blade end.Lock helical blade 27 also has the trailing edge of scanning 217, but they in shape with as shown in Figure 21 main helical blade 17 to scan trailing edge 217 different.
The trailing edge 217 of lock helical blade 27 is shown in party upstream in Figure 21 and Figure 22 and is bent upwards, opposite with downstream direction D.These upstream crooked trailing edges 217 have inner radial trailing edge 230 and radially outer trailing edge 232, and this inner radial trailing edge 230 and radially outer trailing edge 232 scan backward along trailing edge 217 point of distance 235 on downstream that radially is positioned between brake wheel hub 53 and the expander housing 209.
In gaseous environment, high Mach number can limit high wheel speed work.For example, 0.5 air inlet Mach number and grade are that the wheel speed of the correction of 1000ft/sec (feet per second) will produce ultrasonic relevant blade inlet Mach number.Expectation be with in addition be higher than the wheel speed work of 1000ft/sec because can shorten machinery or member this moment.When the relevant Mach number of inlet during near velocity of sound, the factor of shock at entry and obstruction will seriously limit utilizes the plane rotor end to carry out the benefit of high speed operation.The leading edge of scanning through inlet outlet flowpath segment 76 helps avoid these problems.
Axial flow positive displacement engine component is provided at the engine design that each proparea has high quality stream and has the potentiality of efficient compression and expansion.The positive displacement member designs also can provide and the proportional volume mass velocity of rotating speed, and the almost constant compression force ratio in the broad velocity range.This combination provides the chance of improving member and levels of system performance that is better than competitive turbine components for the thermodynamic process of compression, burning and expansion.
As shown in Figure 23 to Figure 26, for turbine or expander 88, the member 3 of axial flow positive displacement gas turbine engine disclosed herein can have more than one main rotor.First structure that has two main rotors 12 and a gate rotor 7 in rotor assembly 15 has been shown among Figure 23.Figure 24 illustrates second structure that in rotor assembly 15, has two main rotors 12 and two gate rotors 7.In Figure 25, show the vane collocation of first structure that in rotor assembly 15, has two main rotors 12 and a gate rotor 7 with axial cross section.All main axiss 16 and lock axis 18 that Figure 23 and Figure 25 also show main rotor 12 and gate rotor 7 all are coplanes.As alternative, as shown in Figure 26, the main axis 16 of main rotor 12 and gate rotor 7 and lock axis 18 can be not in one plane but be parallel.
Although having described, this paper takes it is the content of the preferred embodiments of the present invention and exemplary embodiment as; but those skilled in the art will be clear that according to the instruction content of this paper; the present invention can carry out other and revise, and expects that therefore all such modifications that will fall in connotation of the present invention and the scope all are protected in claims.What therefore, expectation was protected by patent certificate is as defined in the claim and the present invention who is distinguished.
Claims (10)
1. the member (3) of an axial flow positive displacement gas turbine engine comprises:
Rotor assembly (15), it exports (22) from the axially isolated axial flow that holoaxial streaming inlet (20) extends to the downstream,
Described rotor assembly (15) comprises main rotor (12) and one or more gate rotor (7),
Described main rotor (12) rotates with parallel main axis (16) and lock axis (18) that described gate rotor (7) can center on described main rotor (12) and described gate rotor (7) respectively,
Described main rotor (12) and described gate rotor (7) have intermeshing main helical blade (17) and the lock helical blade (27) that centers on described main axis (16) and described lock axis (18) coiling respectively, and
Described main helical blade (17) and described lock helical blade (27) are from being defined as around the annular main wheel hub (51) and the radially extension outwards of circular brake wheel hub (53) of the lock axis (18) of the main axis (16) of described main rotor (12) and described gate rotor (7).
2. the member (3) of axial flow positive displacement gas turbine engine according to claim 1 is characterized in that, described member (3) also comprises:
The intermediate portion (170) of described main helical blade (17), it extends vertically and downstream, and has from the radially outwards measured overall diameter of described main wheel hub (51) to height (H),
Inlet changeover portion (28) in the axial the place ahead and the upstream of described middle body (170), and
Described main helical blade (17) carries out the transition to fully the blade profile that launches from 0 radial height in described inlet changeover portion (28), the described blade profile that launches fully has at downstream direction (D) to be gone up from the radially measured overall diameter of described main wheel hub (51) to height (H).
3. the member (3) of axial flow positive displacement gas turbine engine according to claim 1 is characterized in that, described member (3) also comprises:
At the axial rearward direction of described middle body (170) and the outlet changeover portion (30) in downstream, and
Described main helical blade (17) carries out the transition at downstream direction (D) upward from 0 radially measured radial height of described main wheel hub (51) to the blade profile that launches fully of height (H) from having described overall diameter in described outlet changeover portion (30).
4. the member (3) of axial flow positive displacement gas turbine engine according to claim 1 is characterized in that, described member (3) also comprises the gearing (80) that described main rotor (12) and described gate rotor (7) are linked together with gear.
5. the member (3) of axial flow positive displacement gas turbine engine according to claim 2 is characterized in that, described member (3) also comprises:
Stream (40), it is disposed radially between described main wheel hub (51) and described brake wheel hub (53) and described housing (9), and extends to described axial flow outlet (22) vertically downstream from described axial flow inlet (20);
Described main helical blade (17) and described lock helical blade (27) can rotate in described stream (40);
Described stream (40) comprises inlet flowpath segment (76), the annular central flowpath segment (70) that is arranged in the described inlet changeover portion (28) with crossfire relation downstream, and is arranged on the outlet flowpath segment (78) in the described outlet changeover portion (30), and
The annular entry area (AI) of described inlet flowpath segment (76) is less than the annular exit area (AO) of described inlet flowpath segment (76).
6. the member (3) of axial flow positive displacement gas turbine engine according to claim 5 is characterized in that, described member (3) also comprises the outlet flowpath segment (78) with the circular crosssection area (CA) that reduces along described downstream direction (D).
7. the member (3) of axial flow positive displacement gas turbine engine according to claim 1, it is characterized in that, described member (3) also comprises: the main helical blade (17) of described rotor assembly (15), and it has the different first main slope (34) and second that reverses respectively and leads and reverse slope (36) in first section (24) and second section (26); And the lock helical blade (27) of described rotor assembly (15), it has in described first section (24) and described second section (26) respectively, and the first different locks reverses slope (32) and second lock reverses slope (35).
8. the compressor (8) of an axial flow positive displacement gas turbine engine comprises:
Rotor assembly (15), it exports (22) from the axially isolated axial flow that holoaxial streaming inlet (20) extends to the downstream,
Described rotor assembly (15) comprises main rotor (12) and one or more gate rotor (7),
Described main rotor (12) rotates with parallel main axis (16) and lock axis (18) that described gate rotor (7) can center on described main rotor (12) and described gate rotor (7) respectively,
Described main rotor (12) and described gate rotor (7) have intermeshing main helical blade (17) and the lock helical blade (27) that centers on described main axis (16) and described lock axis (18) coiling respectively,
Described main helical blade (17) and described lock helical blade (27) are from being defined as around the annular main wheel hub (51) and the radially extension outwards of circular brake wheel hub (53) of the lock axis (18) of the main axis (16) of described main rotor (12) and described gate rotor (7), the main helical blade (17) of described rotor assembly (15) has the different first main slope (34) and second that reverses respectively in first section (24) and second section (26) leads and reverses slope (36), and the lock helical blade (27) of described rotor assembly (15) has in described first section (24) and described second section (26) respectively that the first different locks reverses slope (32) and second lock reverses slope (35), and
Described first main slope (34) and described first lock of reversing reverses slope (32) and leads less than described second respectively and reverse slope (36) and described second lock reverses slope (35).
9. the expander (88) of an axial flow positive displacement gas turbine engine comprises:
Rotor assembly (15), it exports (22) from the axially isolated axial flow that holoaxial streaming inlet (20) extends to the downstream,
Described rotor assembly (15) comprises main rotor (12) and one or more gate rotor (7),
Described main rotor (12) rotates with parallel main axis (16) and lock axis (18) that described gate rotor (7) can center on described main rotor (12) and described gate rotor (7) respectively,
Described main rotor (12) and described gate rotor (7) have intermeshing main helical blade (17) and the lock helical blade (27) that centers on described main axis (16) and described lock axis (18) coiling respectively,
Described main helical blade (17) and described lock helical blade (27) are from being defined as around the annular main wheel hub (51) and the radially extension outwards of circular brake wheel hub (53) of the lock axis (18) of the main axis (16) of described main rotor (12) and described gate rotor (7), the main helical blade (17) of described rotor assembly (15) has the different first main slope (34) and second that reverses respectively in first section (24) and second section (26) leads and reverses slope (36), and the lock helical blade (27) of described rotor assembly (15) has in described first section (24) and described second section (26) respectively that the first different locks reverses slope (32) and second lock reverses slope (35), and
Described first main slope (34) and described first lock of reversing reverses slope (32) and leads greater than described second respectively and reverse slope (36) and described second lock reverses slope (35).
10. the member (3) of an axial flow positive displacement gas turbine engine comprises:
Rotor assembly (15), it exports (22) from the axially isolated axial flow that holoaxial streaming inlet (20) extends to the downstream,
Described rotor assembly (15) comprises one or more main rotors (12) and one or more gate rotor (7),
Described main rotor (12) rotates with parallel main axis (16) and lock axis (18) that described gate rotor (7) can center on described main rotor (12) and described gate rotor (7) respectively,
Described main rotor (12) and described gate rotor (7) have intermeshing main helical blade (17) and the lock helical blade (27) that centers on described main axis (16) and described lock axis (18) coiling respectively, and
Described main helical blade (17) and described lock helical blade (27) are from being defined as around the annular main wheel hub (51) and the radially extension outwards of circular brake wheel hub (53) of the lock axis (18) of the main axis (16) of described main rotor (12) and described gate rotor (7).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/347617 | 2008-12-31 | ||
| US12/347,617 US8328542B2 (en) | 2008-12-31 | 2008-12-31 | Positive displacement rotary components having main and gate rotors with axial flow inlets and outlets |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101769165A true CN101769165A (en) | 2010-07-07 |
| CN101769165B CN101769165B (en) | 2014-10-29 |
Family
ID=41697916
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910113700.0A Expired - Fee Related CN101769165B (en) | 2008-12-31 | 2009-12-31 | Positive displacement gas turbine engine with parallel screw rotors |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US8328542B2 (en) |
| EP (1) | EP2204532A3 (en) |
| JP (1) | JP5647411B2 (en) |
| CN (1) | CN101769165B (en) |
| CA (1) | CA2689175C (en) |
| RU (1) | RU2532637C2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454174A (en) * | 2014-10-13 | 2015-03-25 | 罗显平 | Method for improving power take-off power of gas engine |
| CN107617496A (en) * | 2017-11-09 | 2018-01-23 | 张迎新 | A kind of medical waste apparatus for crushing and treating |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013078132A1 (en) * | 2011-11-22 | 2013-05-30 | Vilter Manufacturing Llc | Single screw expander/compressor apparatus |
| US20130247558A1 (en) * | 2012-03-22 | 2013-09-26 | Richard H. Maruya | Heat pump with turbine-driven energy recovery system |
| CN104196571B (en) * | 2014-08-18 | 2017-10-03 | 罗显平 | A kind of method and its device for improving turbine engine efficiency |
| GB2537635A (en) * | 2015-04-21 | 2016-10-26 | Edwards Ltd | Pump |
| CN106678089B (en) * | 2017-02-05 | 2018-04-13 | 罗显平 | A kind of fluid drive and its vehicle |
| FR3065040B1 (en) * | 2017-04-07 | 2019-06-21 | Pfeiffer Vacuum | PUMPING GROUP AND USE |
| CN110005609B (en) * | 2019-01-21 | 2020-04-28 | 合肥通用机械研究院有限公司 | Smooth rotor profile of double-screw vacuum pump and design method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3282495A (en) * | 1964-04-29 | 1966-11-01 | Dresser Ind | Sealing arrangement for screw-type compressors and similar devices |
| US3807911A (en) * | 1971-08-02 | 1974-04-30 | Davey Compressor Co | Multiple lead screw compressor |
| GB2030227A (en) * | 1978-09-20 | 1980-04-02 | Klaey E | Rotary-piston fluid-machines |
| EP0484885B1 (en) * | 1990-11-06 | 1995-06-14 | Honda Giken Kogyo Kabushiki Kaisha | Screw type pump |
| US6508639B2 (en) * | 2000-05-26 | 2003-01-21 | Industrial Technology Research Institute | Combination double screw rotor assembly |
| CN1987065A (en) * | 2005-12-19 | 2007-06-27 | 通用电气公司 | Axial flow progressive cavity type gas generator |
Family Cites Families (40)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2481527A (en) | 1944-06-29 | 1949-09-13 | Jarvis C Marble | Rotary multiple helical rotor machine |
| US2652192A (en) | 1947-06-13 | 1953-09-15 | Curtiss Wright Corp | Compound-lead screw compressor or fluid motor |
| FR1500160A (en) * | 1966-07-29 | 1967-11-03 | Improvements to compressors and rotary motors | |
| SE374589B (en) | 1973-07-20 | 1975-03-10 | Atlas Copco Ab | |
| US4088427A (en) | 1974-06-24 | 1978-05-09 | Atlas Copco Aktiebolag | Rotors for a screw rotor machine |
| JPS56121801A (en) * | 1980-02-27 | 1981-09-24 | Hitachi Ltd | Screw hydraulic machine applied to gas |
| SU956840A1 (en) | 1981-02-27 | 1982-09-07 | Предприятие П/Я А-3884 | Screw compressor |
| ZA852093B (en) | 1984-03-21 | 1986-05-28 | Wassan Pty Ltd | Fluid motor or pump |
| GB2165890B (en) | 1984-10-24 | 1988-08-17 | Stothert & Pitt Plc | Improvements in pumps |
| SU1620681A1 (en) * | 1989-01-12 | 1991-01-15 | Ленинградский технологический институт холодильной промышленности | Method of compressing gas in screw compressor |
| SE8904359L (en) * | 1989-12-22 | 1991-06-23 | Opcon Autorotor Ab | SCREW COMPRESSOR FOR COMBUSTION ENGINES |
| CA2058325A1 (en) * | 1990-12-24 | 1992-06-25 | Mark E. Baran | Positive displacement pumps |
| US5167489A (en) | 1991-04-15 | 1992-12-01 | General Electric Company | Forward swept rotor blade |
| JPH05164070A (en) * | 1991-12-17 | 1993-06-29 | Daikin Ind Ltd | Fluid compressor |
| JPH05195957A (en) * | 1992-01-23 | 1993-08-06 | Matsushita Electric Ind Co Ltd | Vacuum pump |
| GB9203521D0 (en) | 1992-02-19 | 1992-04-08 | Fleming Thermodynamics Ltd | Screw rotors type machine |
| KR100190310B1 (en) * | 1992-09-03 | 1999-06-01 | 모리시따 요오이찌 | Two stage primary dry pump |
| JP3593365B2 (en) | 1994-08-19 | 2004-11-24 | 大亜真空株式会社 | Variable helix angle gear |
| US6105378A (en) | 1995-10-30 | 2000-08-22 | Shaw; David N. | Variable capacity vapor compression cooling system |
| US5775117A (en) | 1995-10-30 | 1998-07-07 | Shaw; David N. | Variable capacity vapor compression cooling system |
| US6217304B1 (en) | 1995-10-30 | 2001-04-17 | David N. Shaw | Multi-rotor helical-screw compressor |
| US6003324A (en) | 1997-07-11 | 1999-12-21 | Shaw; David N. | Multi-rotor helical screw compressor with unloading |
| ATE266800T1 (en) | 1998-10-23 | 2004-05-15 | Busch Sa Atel | TWIN CONVEYOR SCREW ROTORS |
| FI111023B (en) | 1998-12-30 | 2003-05-15 | Sulzer Pumpen Ag | Method and apparatus for pumping material and rotor used in connection with the apparatus |
| US6195983B1 (en) | 1999-02-12 | 2001-03-06 | General Electric Company | Leaned and swept fan outlet guide vanes |
| ATE264457T1 (en) * | 1999-07-19 | 2004-04-15 | Sterling Fluid Sys Gmbh | DISPLACEMENT MACHINE FOR COMPRESSIBLE MEDIA |
| GB9930556D0 (en) | 1999-12-23 | 2000-02-16 | Boc Group Plc | Improvements in vacuum pumps |
| CZ288117B6 (en) * | 2000-02-18 | 2001-04-11 | Perna Vratislav | Device with spiral teeth in interaction with each other |
| CH694339A9 (en) | 2000-07-25 | 2005-03-15 | Busch Sa Atel | Twin screw rotors and those containing Ve rdraengermaschinen. |
| JP3673743B2 (en) | 2001-09-27 | 2005-07-20 | 大晃機械工業株式会社 | Screw type vacuum pump |
| US7008201B2 (en) | 2001-10-19 | 2006-03-07 | Imperial Research Llc | Gapless screw rotor device |
| US6739851B1 (en) | 2002-12-30 | 2004-05-25 | Carrier Corporation | Coated end wall and method of manufacture |
| US6821098B2 (en) | 2003-02-11 | 2004-11-23 | Carrier Corporation | Screw compressor having compression pockets closed for unequal durations |
| US7232297B2 (en) | 2003-05-08 | 2007-06-19 | Automotive Motion Technology Limited | Screw pump |
| WO2005033519A1 (en) | 2003-10-01 | 2005-04-14 | City University | Plural screw positive displacement machines |
| JP2007518918A (en) | 2004-01-14 | 2007-07-12 | エルソム・エンタープライズィズ・リミテッド | Energy conversion method in capacity type rotary screw machine |
| US7178352B2 (en) | 2004-04-08 | 2007-02-20 | Carrier Corporation | Compressor |
| US7121814B2 (en) * | 2004-09-30 | 2006-10-17 | Carrier Corporation | Compressor sound suppression |
| US7530217B2 (en) * | 2005-12-16 | 2009-05-12 | General Electric Company | Axial flow positive displacement gas generator with combustion extending into an expansion section |
| US7854111B2 (en) * | 2008-03-07 | 2010-12-21 | General Electric Company | Axial flow positive displacement turbine |
-
2008
- 2008-12-31 US US12/347,617 patent/US8328542B2/en active Active
-
2009
- 2009-12-15 EP EP09179252.3A patent/EP2204532A3/en not_active Withdrawn
- 2009-12-23 CA CA2689175A patent/CA2689175C/en not_active Expired - Fee Related
- 2009-12-25 JP JP2009293581A patent/JP5647411B2/en not_active Expired - Fee Related
- 2009-12-29 RU RU2009148668/06A patent/RU2532637C2/en not_active IP Right Cessation
- 2009-12-31 CN CN200910113700.0A patent/CN101769165B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3282495A (en) * | 1964-04-29 | 1966-11-01 | Dresser Ind | Sealing arrangement for screw-type compressors and similar devices |
| US3807911A (en) * | 1971-08-02 | 1974-04-30 | Davey Compressor Co | Multiple lead screw compressor |
| GB2030227A (en) * | 1978-09-20 | 1980-04-02 | Klaey E | Rotary-piston fluid-machines |
| EP0484885B1 (en) * | 1990-11-06 | 1995-06-14 | Honda Giken Kogyo Kabushiki Kaisha | Screw type pump |
| US6508639B2 (en) * | 2000-05-26 | 2003-01-21 | Industrial Technology Research Institute | Combination double screw rotor assembly |
| CN1987065A (en) * | 2005-12-19 | 2007-06-27 | 通用电气公司 | Axial flow progressive cavity type gas generator |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454174A (en) * | 2014-10-13 | 2015-03-25 | 罗显平 | Method for improving power take-off power of gas engine |
| CN107617496A (en) * | 2017-11-09 | 2018-01-23 | 张迎新 | A kind of medical waste apparatus for crushing and treating |
| CN107617496B (en) * | 2017-11-09 | 2018-10-16 | 邵海明 | A kind of medical waste apparatus for crushing and treating |
Also Published As
| Publication number | Publication date |
|---|---|
| JP5647411B2 (en) | 2014-12-24 |
| EP2204532A2 (en) | 2010-07-07 |
| CN101769165B (en) | 2014-10-29 |
| CA2689175C (en) | 2017-05-09 |
| JP2010164047A (en) | 2010-07-29 |
| CA2689175A1 (en) | 2010-06-30 |
| RU2009148668A (en) | 2011-07-10 |
| EP2204532A3 (en) | 2014-10-08 |
| US8328542B2 (en) | 2012-12-11 |
| RU2532637C2 (en) | 2014-11-10 |
| US20100166591A1 (en) | 2010-07-01 |
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